Satellite orbit motion ground simulation system and method

The invention relates to a satellite orbit motion ground simulation system based on air-flotation theory, comprising an air-flotation stage, an air foot on the air-flotation stage, a high-pressure air source connected with the air foot and a center gravitation simulator, wherein the center gravitation simulator comprises a first center axle, vertically mounted in the middle of the air-flotation stage; a first magnet, horizontally mounted on the first center axle; a second center axle, vertically mounted on the air foot; a second magnet, horizontally mounted on the second center axle wherein the magnetometric resultant force line of the first magnet and the second magnet passes through the connection line of the first, second center axle. The method using the said system comprises the following steps: cutting over the high-pressure air source; making a satellite simulator float by a layer of air membrane generated between the air foot and air-flotation stage; providing a movement velocity ...

On-line restoration method of permanent fault circuit of reconfigurable satellite-borne computer

The invention provides an on-line restoration method of a permanent fault circuit of a reconfigurable satellite-borne computer, which relates to the technical fields of space flight and aviation and solves the problem that irreparable damage generated by an FPGA circuit in a traditional reconfigurable satellite-borne computer under the influence of space radiation causes a permanent circuit faultdirectly. The on-line restoration method comprises the following steps of: firstly, determining an FPGA circuit generating a permanent circuit fault by a radiation hardening processor, then starting using the other FPGA circuit to work by the radiation hardening processor and finally, carrying out on-line restoration on the FPGA circuit generating the permanent circuit fault by the radiation hardening processor. The invention is suitable for reconfigurable satellite-borne computers.

Externally loading centroid adjuster of air-floating rotating table

Spacecraft attitude control semi-physical simulation system

The invention discloses a spacecraft attitude control semi-physical simulation system which relates to a spacecraft control semi-physical simulation system. The invention solves the problems of poor universality and systematicness in the prior spacecraft attitude control semi-physical simulation system. The simulation signal input or output end of a real-time simulation machine of the system is connected with the simulation signal output or input end of an onboard spacecraft computer; the wireless signal output or output end of a system wireless communication module is connected with the wireless signal input or output end of the real-time simulation machine; the signal output end of a ground wireless communication module is connected with the signal input end of a data storage module; the data signal output end 1 of the data storage module is connected with the data signal input end of a flight simulation display module; and the data signal output end 2 of the data storage module is connected ...

Satellite posture all-round controlling method based on magnetic moment device and flywheel

The invention discloses a satellite posture all-round controlling method based on a magnetic moment device and a flywheel, relating to an all-round posture controlling method for completing a satellite orbit-injection phase by using the magnetic moment device and the flywheel. The invention solves the problems of low reliability and short service life of the traditional satellite posture all-round controlling technology. The satellite posture all-round controlling method comprises the following steps of: 1, setting controller parameters according to the requirement of a control system; 2, measuring a geomagnetic field intensity vector Bb, a satellite angular velocity vector Wb and a solar azimuth, and sending the measured data to a satellite controller; 3, calculating an expected control moment vector Tm and a control magnetic moment vector Mm, and sending the control magnetic moment vector Mm to the magnetic moment device; 4, acquiring an effective solar azimuth vector Alfa; 5, calculating ...

Face-beautifying fragrant handkerchief and making method thereof

The present invention discloses a face-beautifying perfume bag and its preparation method. It is made up by using leonurus, aconite/typhonium tuber, asarum, bletilla tuber, mercurous chloride and talcum powder as raw material, and processing them through such processes of cleaning, dust-removing, drying, pulverizing, mixing and bagging. Said invented product possesses good effect of beautifying face, protecting skin and delaying its senitity.

Satellite load self-power on/off control module

The invention discloses a satellite load self-power on/off control module, relates to the technical field of aerospace fault treatment, and solves the problem that the traditional satellites cannot perform power off and power on or unlock the locked fault during the single-particle locked fault. A power module is connected with the drain of an NMOS tube; the source of the NMOS tube is grounded; a cathode of a diode is connected with the grid of the NMOS tube, and an anode of the diode is connected with the source of a PMOS tube; and the power module is connected with the drain of the PMOS tube. One end of a first capacitor is connected between the grid of the NMOS tube and the cathode of the diode, and the other end of the first capacitor is grounded; one end of a first resistor is connected between the anode of the diode and the source of the PMOS tube, and the other end of the first resistor is grounded; a second capacitor and a second resistor are connected in parallel between a power ...

Satellite dynamics simulation system and method based on satellite dynamics model library

A satellite dynamics simulation system and method based on a satellite dynamics model library relates to the technical field of computer simulation. The invention solves the problems of high development cost and long cycle because the existing dynamics simulation systems need repetitive building of simulation models to complete modeling. The satellite dynamics simulation system comprises a satellite dynamics model library and a model management system, wherein the satellite dynamics model library is used for providing various orbit dynamics simulation models, various spatial environment simulation models, various attitude dynamics simulation models, various sensor measurement simulation models and various basic algorithm simulation models; and the model management system is used for calling and controlling various models in the satellite dynamics model library according to the simulation tasks so as to realize satellite dynamics simulation. The invention is application to satellite simulation ...

Formation satellite attitude cooperative control simulating device and simulation verification method thereof

The invention relates to a formation satellite attitude cooperative control simulating device and a simulation verification method thereof, which belong to the field of aerospace and aims and solve the problem that a traditional satellite attitude cooperative control problem only can be stopped on the level of mathematical simulation. The device comprises a basic platform unit, n air-floating rotary table systems, a camera positioning system and a ground control unit, and the simulation verification method which is carried out on the basis of the device comprises the following steps of: issuing a control instruction by a ground control computer according to a scheme and computing control torque by a PC104 simulation computer; designing a torque distribution method for a thruster, and carrying out simulation by an air-floating rotary table according to the set scheme; transmitting the information of a camera after photo taking to a photo processing computer to obtain angle information; acquiring ...

Satellite load self-power on/off control module

The invention discloses a satellite load self-power on/off control module, relates to the technical field of aerospace fault treatment, and solves the problem that the traditional satellites cannot perform power off and power on or unlock the locked fault during the single-particle locked fault. A power module is connected with the drain of an NMOS tube; the source of the NMOS tube is grounded; acathode of a diode is connected with the grid of the NMOS tube, and an anode of the diode is connected with the source of a PMOS tube; and the power module is connected with the drain of the PMOS tube. One end of a first capacitor is connected between the grid of the NMOS tube and the cathode of the diode, and the other end of the first capacitor is grounded; one end of a first resistor is connected between the anode of the diode and the source of the PMOS tube, and the other end of the first resistor is grounded; a second capacitor and a second resistor are connected in parallel between a power ...

Integrated actuating mechanism for realizing satellite attitude control and electric energy acquisition by combining liquid momentum wheel loop with solar array

The invention discloses an integrated actuating mechanism for realizing satellite attitude control and electric energy acquisition by combining a liquid momentum wheel loop with a solar array, which relates to an integrated actuating mechanism for satellite attitude control and electric energy acquisition. The integrated actuating mechanism is characterized in that solar-cell panels are respectively laid on a rolling surface, a pitching surface and a yaw surface of a satellite body so as to form the solar array; the liquid momentum wheel loop is filled with a liquid working medium flow; N storage tanks are fixed on the satellite body, and a liquid discharge outlet of each storage tank is communicated with the liquid momentum wheel loop by a fluid driving device. The integrated actuating mechanism disclosed by the invention is suitable for satellite attitude control and electric energy acquisition.

Multi-core onboard spacecraft computer based on FPGA

The invention relates to a multi-core satellite-bone computer, belonging to the data processing technical field of aerospace and aiming at solving the problem of slow processing speed of the satellite-bone computer by adopting an ASIC software realization mode. The satellite-bone computer comprises an FPGA based on an SRAM, n PROMS, n SRAMS, an anti-fuse FPGA and a configuration NOR type flash memory, wherein the FPGA based on the SRAM forms a multi-core structure with n processors, the anti-fuse FPGA comprises a read-back brush write interface circuit, a monitoring circuit and a control circuit, the monitoring circuit monitors the health state of the n processors, if an abnormal part needs reconstruction, the read-back brush write interface circuit reads the configuration file of the FPGA based on the SRAM at set speed, compares the configuration file of the FPGA with an original configuration file, and reconstructs the error parts if different. The multi-core satellite-bone computer can ...

Design method of inter-satellite communication system of formation small satellites based on Petri net

The invention relates to a design method of an inter-satellite communication system of formation small satellites based on Petri net, belonging to the technical field of satellite communication. The invention is characterized by modeling the inter-satellite communication system of the formation small satellites by adopting the Petri net, and constructing a simulation platform of the inter-satellite communication system of the formation small satellites, thereby providing the design method of the inter-satellite communication system based on the simulation platform. The design method of the inter-satellite communication system of the formation small satellites based on the Petri net divides system design into five stages which are respectively a task originating and analysis stage, a task decomposition and design stage, a model or subsystem design stage, an integrated simulation verification stage and a result evaluation stage. The invention has the effects and benefit of using an advanced ...

Flywheel based attitude maneuvering control device and method for successive approaching of satellite rounding instantaneous Euler shaft

The invention discloses flywheel based attitude maneuvering control device and method for successive approaching of a satellite rounding an instantaneous Euler shaft and relates to control device and method for satellite attitude adjustment. The invention is provided for solving the problems of great fuel consumption, short service life of a satellite, complex configuration of an air injecting control system and difficult reduction of size and weight of the satellite existing in the realization of satellite wide-angle attitude maneuvering by adopting air injecting control. The method comprises the following steps of: setting a parameter of the control device according to the system requirement of the control device and obtaining attitude deviation angular velocity according to a motion equation; and expressing a relationship of the instantaneous Euler shaft and a deviation angle of the current attitude and a target attitude of the satellite by an attitude error quaternion to obtain a control ...

Self-adaption on-board computer based on FPGA and method thereby for realizing dynamic allocation of internal resource

The invention discloses a self-adaption on-board computer based on FPGA and a method thereby for realizing dynamic allocation of internal resource, belonging to the technical field of space flight and aviation data processing, and solving the problem that the traditional reconfigurable on-board computer can not effectively manage reconfigurable FPGA resource. The on-board computer of the invention is realized by SRAM-type FPGA, the internal source of the SRAM-type FPGA comprises a main control unit and a reconfigurable unit array composed of n reconfigurable units with exactly same size, and the SRAM-type FPGA supports parts of reconfigurable technology. The method for realizing dynamic allocation of internal resource of the invention is characterized in that the main control unit configures the reconfigurable unit in the idle condition into a corresponding hardware circuit according to a hardware circuit needed by threads when the on-board computer starts a thread; when the thread ends ...

Low-orbit aircraft based on aerodynamic attitude control and attitude control method thereof

The invention provides a low-orbit aircraft based on aerodynamic attitude control and an attitude control method thereof, relating to the low-orbit aircraft and the attitude control method thereof and solving the problems of high fuel consumption of the current low-orbit aircraft and the attitude control method thereof and short on-orbit service life of the aircraft. The low-orbit aircraft comprises an aircraft body, a pair of pitching-direction attitude control aerodynamic auxiliary boards, a pair of yawing-direction attitude control aerodynamic auxiliary boards, a first rotating mechanical arm, a second rotating mechanical arm, a third rotating mechanical arm and a fourth rotating mechanical arm. The attitude control method of the low-orbit aircraft comprises the following steps of: acquiring the current attitude angle and the target attitude angle of the low-orbit aircraft, obtaining a member to be deflexed and an angle through combining with aircraft attitude dynamics model and a kinematics ...

Method for realizing precision positioning utilizing electric machine

Method for controlling rigid spacecraft for target attitude tracking

The invention relates to a method for controlling a rigid spacecraft for target attitude tracking, and belongs to the technical field of the high-precision and high-stability attitude tracking control of spacecrafts. The method solves the problem that when the attitude tracking spacecraft runs in a low orbit in outer space, the conventional control method cannot eliminate the inherent flutter of a sliding mode variable structure. The method comprises the following steps: 1, establishing a kinetic model and a kinematic model of the rigid spacecraft; 2, setting an attitude tracking error and anexpected attitude parameter of the rigid spacecraft, and combining the attitude tracking error and the expectation attitude parameter with the kinetic model and the kinematic model to establish a mathematical model for the attitude tracking; 3, adopting a control algorithm of a sliding mode variable structure controller to adjust a control law of the mathematical model which is established in thestep ...

Finite state machine with radiating resistant function for reconfigurable satellite-loaded computer

The invention discloses a finite state machine with a radiating resistant function for a reconfigurable satellite-loaded computer and relates to the technical field of aerospace. The invention solves the problem of integral function invalidation of the reconfigurable satellite-loaded computer because the traditional reconfigurable satellite-loaded computer is short of resistance on space radiation. The finite state machine comprises an FPGA (Field Programmable Gate Array), a counter circuit and a timer circuit, wherein the FPGA comprises a selector, a register, a Hamming code checking circuit, a switch circuit and an in-chip dual-port RAM (Random Access Memory); the timer circuit is respectively connected with the counter circuit, the selector and the switch circuit; the counter circuit is also connected with the selector; the selector is also connected with the Hamming code checking circuit, the in-chip dual-port RAM and the register; the register is also connected with the in-chip dual-port ...

Liquid circuit based gyroscopic moment generating device and satellite attitude control method

The invention relates to a liquid circuit based gyroscopic moment generating device and a satellite attitude control method, relating to a liquid control moment gyroscope device and the satellite attitude control method and solving the problems of poor safety and short service life of the traditional method and poor integral satellite attitude control effect caused in such a way that the traditional method is easy to influence by cosmic radiation. A device 1 and an annular rigid pipeline surround the outer side of a satellite body, and the annular rigid pipeline rotates along an OY axis and an OZ axis through two motors. The satellite attitude control method comprises the following steps of: generating gyroscopic moments along the directions of the OY axis, the OZ axis, a -OY axis and a -OZ axis by controlling the two motors; and generating the gyroscopic moments along the directions of an OX axis and a -OX axis by controlling fluid pumps, therefore the control of satellite three-axisattitudes ...

Gastrointestinal mucosa nutritive protective agent and its preparing technology

The present invention discloses a nutritive protective agent for gastrointestinal mucosa and its preparation process. Said protective agent is made up by using ass hide glue, honey-fried astragalus root, codonopsis root, white peony root, cinnamon bark,, bletilla tuber, cuttlefish bone and honey-fried licorice, etc. through such processes of weighing, proportioning, mixing, drying and pulverizing. Said invented protective agent has the function of boosting qi and nourishing stomach, harmonizing qi and blood, improving gastrointestinal function and relieving inflammation and stopping pain.

Image motion compensation method for space optical remote sensor

The present invention provides an image motion compensation method for a space optical remote sensor, relating to an image motion compensation method and solving the problem that the current image motion velocity vector calculation method used in image motion compensation cannot satisfy complex imaging tasks and the calculation result is not accurate. The process of the image motion compensation method is as follows: creating five coordinate systems starting from ground targets to image points, transferring the coordinates for a plurality of times according to the rotation and translation principles among vectors, describing the positions of the targets and the image points in the camera coordinate systems, obtaining the image motion velocity vector calculation formula and the calculation method when the satellite forms images of the targets, then obtaining the image motion velocity vector used in the image motion compensation of the space optical remote sensor. The image motion compensation ...

Finite state machine with radiating resistant function for reconfigurable satellite-loaded computer

The invention discloses a finite state machine with a radiating resistant function for a reconfigurable satellite-loaded computer and relates to the technical field of aerospace. The invention solves the problem of integral function invalidation of the reconfigurable satellite-loaded computer because the traditional reconfigurable satellite-loaded computer is short of resistance on space radiation. The finite state machine comprises an FPGA (Field Programmable Gate Array), a counter circuit and a timer circuit, wherein the FPGA comprises a selector, a register, a Hamming code checking circuit, a switch circuit and an in-chip dual-port RAM (Random Access Memory); the timer circuit is respectively connected with the counter circuit, the selector and the switch circuit; the counter circuit is also connected with the selector; the selector is also connected with the Hamming code checking circuit, the in-chip dual-port RAM and the register; the register is also connected with the in-chip dual-port ...

On-line restoration method of permanent fault circuit of reconfigurable satellite-borne computer

The invention provides an on-line restoration method of a permanent fault circuit of a reconfigurable satellite-borne computer, which relates to the technical fields of space flight and aviation and solves the problem that irreparable damage generated by an FPGA circuit in a traditional reconfigurable satellite-borne computer under the influence of space radiation causes a permanent circuit fault directly. The on-line restoration method comprises the following steps of: firstly, determining an FPGA circuit generating a permanent circuit fault by a radiation hardening processor, then starting using the other FPGA circuit to work by the radiation hardening processor and finally, carrying out on-line restoration on the FPGA circuit generating the permanent circuit fault by the radiation hardening processor. The invention is suitable for reconfigurable satellite-borne computers.

Multi-core onboard spacecraft computer based on FPGA

The invention relates to a multi-core satellite-bone computer, belonging to the data processing technical field of aerospace and aiming at solving the problem of slow processing speed of the satellite-bone computer by adopting an ASIC software realization mode. The satellite-bone computer comprises an FPGA based on an SRAM, n PROMS, n SRAMS, an anti-fuse FPGA and a configuration NOR type flash memory, wherein the FPGA based on the SRAM forms a multi-core structure with n processors, the anti-fuse FPGA comprises a read-back brush write interface circuit, a monitoring circuit and a control circuit, the monitoring circuit monitors the health state of the n processors, if an abnormal part needs reconstruction, the read-back brush write interface circuit reads the configuration file of the FPGA based on the SRAM at set speed, compares the configuration file of the FPGA with an original configuration file, and reconstructs the error parts if different. The multi-core satellite-bone computercan ...

Flywheel based attitude maneuvering control device and method for successive approaching of satellite rounding instantaneous Euler shaft

The invention discloses flywheel based attitude maneuvering control device and method for successive approaching of a satellite rounding an instantaneous Euler shaft and relates to control device and method for satellite attitude adjustment. The invention is provided for solving the problems of great fuel consumption, short service life of a satellite, complex configuration of an air injecting control system and difficult reduction of size and weight of the satellite existing in the realization of satellite wide-angle attitude maneuvering by adopting air injecting control. The method comprises the following steps of: setting a parameter of the control device according to the system requirement of the control device and obtaining attitude deviation angular velocity according to a motion equation; and expressing a relationship of the instantaneous Euler shaft and a deviation angle of the current attitude and a target attitude of the satellite by an attitude error quaternion to obtain a control ...

Method for calculating interface thermal resistance of silicon and germanium super crystal lattice material

The invention provides a method for calculating interface thermal resistance of a silicon and germanium super crystal lattice material and relates to calculation of interface thermal resistance of the silicon and germanium super crystal lattice material and solves the problem that currently theories and experimental methods can not be employed to accurately analyze heat-transfer mechanism of the silicon and germanium super crystal lattice material. The method comprises the following steps: A. establishing a nonequilibrium state molecular dynamics model for the silicon and germanium super crystal lattice material; B. setting initial state of heat conduction model particle, adjusting system temperature to required temperature and demarcating speed of the particle in the silicon and germanium super crystal lattice material at required temperature; C. confirming interparticle action potential energy; D.calculating interparticle acting force of the silicon and germanium super crystal lattice ...